FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
6th Edition
ISBN: 9781265141387
Author: Anderson
Publisher: MCG
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Chapter 5, Problem 5.3P

The measured lift slope for the NACA 23012 airfoil is 0.1080 degree 1 , and α L = 0 = 1.3 ° . Consider a finite wing using this airfoil, with A R = 8 and taper ratio = 0.8 . Assume that δ = τ . Calculate the lift and induced drag coefficients for this wing at a geometric angle of attack = 7 ° .

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A shaft is loaded in bending and torsion such that Ma = 70 N·m, T₁ = 45 N · m, M = 55 N. m, and T = 35 N m. For the shaft, S₁ = 700 MPa and S = 560 MPa, and a fully corrected endurance limit of S₂ = 210 MPa is assumed. Let K = 2.2 and K = 1.8. With a Se design factor of 2.0 determine the minimum acceptable diameter of the shaft using the a) DE- Goodman b) DE-Morrow c) DE-Gerber d) DE-SWT

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